Aerodynamic design optimization of control surfaces for a tailless aircraft at high angles of attack

Abstract

The main purpose is to perform design optimization of control surfaces for a tailless aircraft at high angle of attack condition. In order to capture flow phenomena of leading edge separation on the delta wing type of innovative control effector (ICE) configuration at high angle of attack, the panel method with time-marching wake model is developed. An efficient global optimization (EGO) framework is developed to design control surfaces of the ICE configruation for high aerodynamic performance and good rolling performance. The design results will be included in the manuscript of final paper.